JPH0719121A - Ramjet - Google Patents

Abstract

PURPOSE:To improve a charging ratio and reduce weight by arranging combustion assistant which generates high temperature gas on a combustible gas flow passage communicated with a main combustion chamber of a combustible gas generation chamber in which a sustainer propellant is charged, and thereby enabling charge of only a booster propellant in the main combustion chamber. CONSTITUTION:In a ramjet 1, a booster propellant 2 in a main combustion chamber 3 is ignited by an ignition device 12 for combustion. Combustion gas is injected from a booster nozzle 9 to start a jumping body for acceleration. A separation joint 11 is separated by a releasing mechanism 7, while the booster nozzle and/or a port cover 8 is removed. A sustainer propellant 4 is ignited in a combustible gas generation chamber 5 is ignited by an ignition device 15 for combustion. When the combustible gas is moved passing through a gas flow passage 5a, a combustion assistant 13 is ignited for combustion. Mixture gas is injected from a gas nozzle 14 into a main combustion chamber 3, mixed with compressed air from an air intake port 6, and injected from a ram jet nozzle 10 for generating thrust.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a ramjet used to obtain the flight thrust of a flying object.

[0002]

2. Description of the Related Art Conventionally, as the above-mentioned ramjet,
For example, there is one shown in FIG.

The ramjet 51 shown in FIG. 3 comprises a main combustion chamber 53 loaded with a booster propellant 52 and a combustible gas generation chamber 55 loaded with a sustainer propellant 54. The combustible gas generation chamber 55 is the main combustion chamber. Provided in front of the chamber 53,
It communicates with the main combustion chamber 53 via a gas nozzle 56.

A plurality of air inlets 57 are provided on the outer periphery of the front portion of the main combustion chamber 53 in the circumferential direction, and a port 53a for connecting the air inlet 57 and the main combustion chamber 53 is provided with a nozzle / It is closed by a port cover 59 that can be opened by the port cover release mechanism 58.

Further, a combustion delay portion 60 having a slower burning speed than the booster propellant 52 is built in the front end portion of the main combustion chamber 53, and the booster propellant 52 is continuously burned even after the final stage of combustion. , The combustible gas generated by the combustion of the sustainer propellant 54 and ejected from the gas nozzle 56, and the air intake port 5
Combustion (so-called secondary combustion) of the mixed gas with the external air introduced while being compressed from 7 is continuously performed.

Further, at the rear end of the main combustion chamber 53, a booster nozzle 62 having a booster propellant ignition device 61,
The ramjet nozzle 63 is concentrically provided via a separation joint 64 which is separated by the operation of the nozzle / port cover release mechanism 58.

On the other hand, a sustainer propellant ignition device 65 is provided in the gas generating chamber 53 loaded with the sustainer propellant 54.

Ramjet 51 having such a structure
In the above, the booster propellant 52 is burned in the main combustion chamber 53 by the ignition by the booster propellant ignition device 61, and the combustion gas is injected from the booster nozzle 62 to obtain thrust to start and accelerate.

Subsequently, at the final stage of combustion of the booster propellant 52, the nozzle / port cover release mechanism 58 is operated,
The booster nozzle 63 is separated at the separation joint 64, and the port cover 59 is removed.

At this time, combustion continues in the combustion delay portion 60, while in the combustible gas generation chamber 55, the sustainer propellant 54 is ignited by the sustainer propellant igniter 65, and the combustion of the sustainer propellant 54 occurs. Combustible gas is generated.

The mixed gas of the combustible gas ejected from the gas nozzle 56 and the air introduced from the air intake 57 and compressed is ignited by the combustion delay portion 60 and burned, and the combustion gas generated thereby is burned. It is designed to obtain thrust by being ejected from 63.

The ramjet 51 described above is described in Japanese Patent Application Laid-Open No. 3-172563.

[0013]

However, in the above-mentioned conventional ramjet 51, although the sufficient flight thrust can be obtained, the combustion delay portion 60 is provided in the main combustion chamber 53.
Due to the internal arrangement, the volume of the main combustion chamber 53 in which the booster propellant 52 is loaded must be increased by at least the volume of the combustion delay portion 60, and therefore the weight is increased accordingly. There is a problem in that the degree of freedom in designing a flying body on which the ramjet 51 is mounted is narrowed, and solving the problem has been a conventional problem.

[0014]

SUMMARY OF THE INVENTION The present invention has been made in view of the above-mentioned conventional problems. It is possible to increase the loading rate of booster propellant to reduce the weight and to expand the degree of freedom in designing a flying vehicle. It is intended to provide a ramjet that is possible.

[0015]

According to the present invention, a main combustion chamber loaded with a booster propellant and a sustainer propellant which communicates with the main combustion chamber and burns after the booster propellant is burned are loaded. In a ramjet in which a combustible gas generation chamber is provided and the combustible gas generated by combustion of the sustainer propellant is mixed with air introduced from the outside and burned in the main combustion chamber, combustible gas generation in which the sustainer propellant is loaded is generated. The combustible gas flow path communicating with the main combustion chamber of the chamber, characterized in that it is provided with a combustion auxiliary agent that ignites by the combustible gas generated by the combustion of the sustainer propellant to generate a high temperature gas, The configuration of this ramjet is used as means for solving the above-mentioned conventional problems.

In the ramjet according to the present invention,
The raw material composition of the booster propellant and the sustainer propellant is not particularly limited.

The raw material used for the combustion auxiliary agent that ignites the combustible gas generated by the combustion of the sustainer propellant to generate a high temperature gas can be selected according to the raw material of the sustainer propellant, the required combustion time, the combustion energy and the like. And, for example, a composite propellant with the addition of aluminum powder and ammonium perchlorate as oxidizing agent can be used.

Further, in some cases, it is possible to increase the loading amount of the sustainer propellant in this machine by adopting the same combustion aid as the sustainer propellant.

[0019]

In the ramjet according to the present invention, when combustion of the booster propellant in the main combustion chamber ends and combustion of the sustainer propellant in the combustible gas generation chamber begins, the combustion auxiliary agent ignites and burns.

Then, the combustible gas generated by the combustion of the sustainer propellant and the high temperature gas generated by the combustion of the combustion auxiliary agent are mixed to form a mixed gas having high combustion energy, and this mixed gas is jetted into the main combustion chamber. However, the combustion (secondary combustion) performed by mixing with the compressed air introduced from the outside in the main combustion chamber is stably connected.

Therefore, since it is only necessary to load the booster propellant into the main combustion chamber, the volume of the main combustion chamber can be adjusted to the required amount of booster propellant, and the loading ratio of booster propellant increases. Therefore, the weight will be reduced.

[0022]

DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will be described below with reference to the drawings.

1 and 2 show an embodiment of a ramjet according to the present invention.

As shown in FIG. 1, this ramjet 1
Comprises a main combustion chamber 3 loaded with booster propellant 2 and a combustible gas generation chamber 5 loaded with sustainer propellant 4.

On the outer periphery of the front portion of the main combustion chamber 3, there are provided air inlets 6 at a plurality of positions in the circumferential direction, and the port 3a connecting the air inlet 6 and the main combustion chamber 3 is a nozzle. /
It is closed by a port cover 8 which can be opened by a port cover release mechanism 7.

A booster nozzle 9 and a ramjet nozzle 10 are concentrically provided at the rear end of the main combustion chamber 3 via a separation joint 11, and the booster nozzle 9 is the nozzle / port cover release mechanism. Separation joint 1 by operation of 7
1 is separated from the ramjet nozzle 10 by separating in the centrifugal direction. This booster nozzle 9 has a booster propellant ignition device 12 at its center.
The booster propellant ignition device 12 is designed to be removed by the combustion gas generated by the combustion of the booster propellant 2 after ignition.

On the other hand, the combustible gas generating chamber 5 is provided in front of the main combustion chamber 3 and communicates with the main combustion chamber 3 via a gas flow path 5a. Combustible gas generated by the combustion of the sustainer propellant 4 flows into the gas passage 5a.
There is provided a combustion auxiliary agent 13 that ignites to generate a high temperature gas when passing through and moving to the main combustion chamber 3. In this embodiment, the combustion aid 13 is composed of an aluminum powder-containing ammonium perchlorate type composite propellant, and the combustion aid 13 is contained in the main combustion chamber 3 of the gas passage 5a.
It is also provided inside the gas nozzle 14 provided on the side.

A sustainer propellant ignition device 15 is provided at the rear end of the combustible gas generating chamber 5.

In the ramjet 1 having the above-mentioned structure, first, when the booster propellant 2 in the main combustion chamber 3 is ignited by the booster propellant ignition device 12, the booster propellant 2 is burned, and this combustion is performed. By ejecting gas from the booster nozzle 9 while removing the booster propellant ignition device 12, the projectile carrying the ramjet 1 starts and accelerates until it reaches a set Mach number required for operation by ram pressure. .

Subsequently, when the set Mach number is reached and the combustion of the booster propellant 2 is completed, as shown in FIG. 2, the separation joint 11 is separated by the operation of the nozzle / port cover release mechanism 7. The booster nozzle 9 is separated and the port cover 8 is removed. At the same time, in the combustible gas generation chamber 5, the sustainer propellant 4 is ignited by the sustainer propellant ignition device 15.

Next, when the sustainer propellant 4 burns and the combustible gas thereof starts moving to the main combustion chamber 3 side through the gas flow path 5a, the combustion aid 13 ignites and burns.

When the combustible gas generated by the combustion of the sustainer propellant 4 passes through the gas passage 5a, the high temperature gas generated by the combustion auxiliary agent 13 is mixed to form a mixed gas having a high combustion energy. From this, the mixed gas is ejected from the gas nozzle 14 into the main combustion chamber 3, and the combustion (secondary combustion) performed by mixing with the compressed air introduced from the air inlet 6 is performed in a stable state. Therefore, the combustion gas generated by this combustion is transferred to the ramjet nozzle 10
Thrust is generated by injecting from.

As described above, the combustion auxiliary agent 13 for continuously burning the mixed gas of the combustible gas generated by the combustion of the sustainer propellant 4 and the air introduced while being compressed from the air intake 6 is the gas flow passage. 5a and the gas nozzle 14, the booster propellant 2 is provided inside the main combustion chamber 3.
Therefore, the loading rate of the booster propellant 2 in the main combustion chamber 3 is increased, and the weight is reduced.

The detailed construction of the ramjet according to the present invention is not limited to the above embodiment.

[0035]

As described above, since the ramjet according to the present invention has the above-mentioned structure, the loading rate of the booster propellant in the main combustion chamber is increased and the weight can be reduced. As a result, An extremely excellent effect that the degree of freedom when designing a flying body equipped with a ramjet can be expanded is brought about.

[Brief description of drawings]

FIG. 1 is a cross-sectional explanatory view showing an embodiment of a ramjet according to the present invention before booster propellant ignition.

FIG. 2 is a cross-sectional explanatory view after completion of combustion of booster propellant in the ramjet shown in FIG.

FIG. 3 is a cross-sectional explanatory view of a conventional ramjet.

[Explanation of symbols]

 1 Ramjet 2 Booster propellant 3 Main combustion chamber 4 Sustainer propellant 5 Combustible gas generation chamber 5a Gas flow path 13 Combustion aid

Claims (1)

[Claims] 1. A main combustion chamber loaded with booster propellant;
A combustible gas generation chamber that is loaded with a sustainer propellant and that communicates with the main combustion chamber and that burns after the combustion of the booster propellant is completed is provided, and the combustible gas generated by the combustion of the sustainer propellant in the main combustion chamber In a ramjet that mixes and burns the air introduced from the outside into the combustible gas flow path communicating with the main combustion chamber of the combustible gas generation chamber loaded with the sustainer propellant, the combustion of the sustainer propellant caused A ramjet characterized by being provided with a combustion auxiliary agent that ignites with combustible gas to generate high-temperature gas.